Abstract: The present invention relates to a device as well as a method for the additive manufacture of components by deposition of material layers by layer-by-layer joining of powder particles to one another and/or to an already produced pre-product or substrate, via selective interaction of the powder particles with a high-energy beam, wherein, for smoothing a surface of the component being produced running crosswise to the deposited material layers in between the deposition of two layers of the component, the complete edge region of the last layer that is applied and that runs along a surface of the component being produced is compacted in a direction of action that has a directional component parallel to the build-up direction of the layers, and/or at least one edge region of a surface of the component is also compacted.

Abstract: The present invention relates to a device as well as a method for the additive manufacture of components by deposition of material layers by layer-by-layer joining of powder particles to one another and/or to an already produced pre-product or substrate, via selective interaction of the powder particles with a high-energy beam, wherein, for smoothing a surface of the component being produced running crosswise to the deposited material layers in between the deposition of two layers of the component, the complete edge region of the last layer that is applied and that runs along a surface of the component being produced is compacted in a direction of action that has a directional component parallel to the build-up direction of the layers, and/or at least one edge region (19) of a surface of the component (3?) is also compacted.

Abstract: A method for determining residual stresses of a component (14), in particular a component of an aircraft engine, while it is being manufactured by an additive manufacturing process. The method includes the following steps: creating at least one local melt pool (26) in a surface (24) of the component (14) to be manufactured after a predetermined portion of the component is completed; optically detecting surface distortions and/or elongations occurring at least in a region around the created melt pool (26); and determining the residual stresses of the component (14) which are present at least in the region around the created melt pool (26) based on the optically detected surface distortions and/or elongations. Further an apparatus for determining residual stresses of a component (14) while it is being manufactured by an additive manufacturing process is provided.

Abstract: The invention relates to a method and device for ascertaining an edge layer characteristic of a component (12), in particular a component (12) for an aircraft engine. In the method, a reference body (22) with a known edge layer characteristic is arranged on the surface of the component (12). An ultrasonic wave (18) is introduced into the surfaces of the component (12) and the reference object (22) by an ultrasonic transmitter (16). An ultrasonic wave (18) resulting from the exchange between the component (12) and the reference body (22) is detected by an ultrasonic detector (20), and an edge layer characteristic of the component (12) is ascertained by an ascertaining device (28) using a difference between the generated ultrasonic wave (18) and the resulting ultrasonic wave (18).

Abstract: Disclosed is a method for the non-destructive testing of workpiece surfaces of a workpiece by means of fluorescent penetrant testing or dye penetrant testing. The method comprises applying a penetrant to the region of the workpiece surface to be examined, thereby allowing the penetrant to penetrate into possible recesses in the workpiece surface, applying a developer to the region of the workpiece surface to be tested; bleaching the penetrant by a gaseous or liquid oxidant; and visually assessing the penetrant that has remained in the recesses present in the workpiece surface.

Abstract: A method for coating a component, in particular a component of a gas turbine or of an aircraft engine, is disclosed. The coating is applied to the component by kinetic cold gas spraying, where prior to the deposition of the coating, the surface of the component to be coated is cleaned and compacted by shot peening with a blasting media. A component produced in this manner is also disclosed.

Abstract: The invention relates to a method for joining two components (10, 12) made of a metal material, which are connected on two mutually associated joining surfaces (14, 16) by means of a joined connection, wherein at least one of the components (10) is strengthened in at least a partial region of the joining surface (14) thereof prior to joining. The invention further relates to a joined connection of two components (10, 12) made of a metal material.

Abstract: The present invention relates to a method and a device for material processing with a high-energy beam (7), with a beam-generating device (4) for generating a high-energy beam and with a component holder (2), in which is disposed the material that is to be processed with the high-energy beam, wherein the beam-generating device and the component holder are disposed or can be disposed relative to one another so that the high-energy beam impinges on the material surface (12) of the material to be processed at an angle not equal to 0° or 180° or a whole-number multiple thereof, and wherein the beam-generating device or at least parts thereof and/or another beam-generating device can be disposed, and/or that the beam-generating device comprises a deflection means (5, 6), so that a high-energy beam (7a) can be aligned parallel to and at a distance from the material surface (12) to be processed.

Abstract: The invention relates to a method and device for ascertaining an edge layer characteristic of a component (12), in particular a component (12) for an aircraft engine. In the method according to the invention, a reference body (22) with a known edge layer characteristic is arranged on the surface of the component (12). At least one ultrasonic wave (18) is introduced into the surfaces of the component (12) and the reference object (22) by means of an ultrasonic transmitter (16). At least one ultrasonic wave (18) resulting from the exchange between the component (12) and the reference body (22) is detected by means of an ultrasonic detector (20), and an edge layer characteristic of the component (12) is ascertained by means of an ascertaining device (28) using a difference between the at least one generated ultrasonic wave (18) and the at least one resulting ultrasonic wave (18).

Abstract: A method for determining residual stresses of a component (14), in particular a component of an aircraft engine, while it is being manufactured by an additive manufacturing process. The method includes the following steps: creating at least one local melt pool (26) in a surface (24) of the component (14) to be manufactured after a predetermined portion of the component is completed; optically detecting surface distortions and/or elongations occurring at least in a region around the created melt pool (26); and determining the residual stresses of the component (14) which are present at least in the region around the created melt pool (26) based on the optically detected surface distortions and/or elongations. Further an apparatus for determining residual stresses of a component (14) while it is being manufactured by an additive manufacturing process is provided.

Abstract: Disclosed is a method for the non-destructive testing of workpiece surfaces of a workpiece by means of fluorescent penetrant testing or dye penetrant testing. The method comprises applying a penetrant to the region of the workpiece surface to be examined, thereby allowing the penetrant to penetrate into possible recesses in the workpiece surface, applying a developer to the region of the workpiece surface to be tested; bleaching the penetrant by a gaseous or liquid oxidant; and visually assessing the penetrant that has remained in the recesses present in the workpiece surface.

Abstract: A component, in particular an engine component, which has at least one mark with a predetermined three-dimensional shape for determining a stress in the component and where the component is constructed by a generative manufacturing method, is disclosed.

Abstract: A method for coating a component, in particular a component of a gas turbine or of an aircraft engine, is disclosed. The coating is applied to the component by kinetic cold gas spraying, where prior to the deposition of the coating, the surface of the component to be coated is cleaned and compacted by shot peening with a blasting media. A component produced in this manner is also disclosed.

Abstract: A component, in particular an engine component, which has at least one mark with a predetermined three-dimensional shape for determining a stress in the component and where the component is constructed by a generative manufacturing method, is disclosed.

Abstract: A device and a method are disclosed for visualizing positions on a surface by means of a marking which is produced by an optically detectable radiation. In order to permit a residue-free marking which can be observed with a camera from partly extremely oblique observation directions, the device has an optical waveguide, which is coupled to a radiation source and whose light output region can be located at a desired position of the surface in order to emit optically detectable radiation at the desired position of the surface through the optical waveguide. As a result, the radiation is emitted at the desired position of the surface in various spatial directions.

Abstract: A method and apparatus for surface hardening a component, particularly an aircraft construction component, is disclosed. A force is applied to the surface of the component, which is made of an intermetallic compound at least in the region of the surface to be hardened. The component is heated at least in the region that is made of the intermetallic compound to a temperature higher than the standard temperature. The temperature is set such that a ductility of the intermetallic compound at the temperature is increased compared to a ductility of the intermetallic compound at the standard temperature. The apparatus includes a hardening tool and a heating device where the component is heated to a temperature higher than the standard temperature and the temperature is set such that a ductility of the intermetallic compound at the temperature is increased compared to a ductility of the intermetallic compound at the standard temperature.

Abstract: The invention relates to a method for joining two components (10, 12) made of a metal material, which are connected on two mutually associated joining surfaces (14, 16) by means of a joined connection, wherein at least one of the components (10) is strengthened in at least a partial region of the joining surface (14) thereof prior to joining. The invention further relates to a joined connection of two components (10, 12) made of a metal material.

Abstract: A device for representing the direction of action (9) of a working mechanism (3), in particular a tool or a radiation source and/or a radiation emitter, for example, of X-rays is provided. The device includes a first light source (4) which is used to produce a first beam (5). In order to represent the direction of action in a continuous manner, at least one additional light source (4?) which is used to produce an additional beam (5?) is provided. The light sources (4, 4?) and the working device (3) can be oriented in such a manner that the first beam (5) and the additional beam (5?) have a flat extension and cut in the direction of action (9) of the working mechanism (3). The invention also relates to a corresponding method.

Abstract: A method and a system for synchronising angles of at least two displaceable working means (2, 2?) at a predetermined point of action (4) is disclosed. The working means are, in particular, a robot-controlled tool or a robot-controlled radiation emitter and/or radiation receiver. In order to synchronise angles in a precise manner, the directions of the action (1, 1?) of the working means (2, 2?) are, in particular represented in a continuous manner, detected and united at a predetermined point of action (4). The angle (a) between the directions of the action (1, 1?) of the working means (2, 2?) is determined by, in particular, an optical angle measurement and is adjusted to a predetermined value.

Abstract: A method and apparatus for surface hardening parts is disclosed. To harden a surface of a part, a relative movement, or advancing motion, is established between the part and at least one sonotrode-like tool which is excited in the ultrasonic frequency range. The tool is aligned during the surface hardening in such a way to the surface of the part to be hardened that a tool axis running in the effective direction of the tool runs at an angle to the surface of the part to be hardened.